CN107202339A - Axially Staged Fuel Injector Assembly - Google Patents
Axially Staged Fuel Injector Assembly Download PDFInfo
- Publication number
- CN107202339A CN107202339A CN201710157101.3A CN201710157101A CN107202339A CN 107202339 A CN107202339 A CN 107202339A CN 201710157101 A CN201710157101 A CN 201710157101A CN 107202339 A CN107202339 A CN 107202339A
- Authority
- CN
- China
- Prior art keywords
- fuel
- fuel injector
- injector assembly
- air
- central body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
A kind of fuel injector assembly (102), it includes the shield (116) for limiting fuel manifold (122) therein.Fuel manifold (122) is fluidly coupled to burning line (106), to receive from it fuel.Fuel injector assembly (102) also includes central body (118) and multiple stators (120), and central body (118) is operably coupled to shield (116) by the plurality of stator (120).Each stator (120) in multiple stators (120) and circumferentially-adjacent stator (120) are circumferentially spaced, to limit at least one path (124) therebetween, and its transmission is passed through for air.Each in multiple stators (120) has at least one outlet opening (128) being in fluid communication with least one path (124) in fuel manifold (122) and at least one path (124), for fuel to the releasing at least one path (124), for being mixed with air.Fuel injector outlet (130) is limited by the inwall (132) of fuel injector assembly (102), and is positioned to fuel air mixture being guided out fuel injector assembly (102).
Description
Technical field
The subject matter disclosed herein is related to fuel injector, the axially staged combustion such as used in gas-turbine unit
Material ejector.
Background technology
Gas turbine generally burns hydrocarbon fuels, and produces air emissions, such as nitrogen oxides (NOx)
With carbon monoxide (CO).The oxidation of dinitrogen in gas turbine depends on the temperature for the gas being located in burner, Yi Jiwei
The residence time of reactant in the highest temperature region in burner.Therefore, the NOx produced by gas turbine amount can lead to
Cross by burner temperature be maintained at produce NOx temperature below, or by the residence time of limited reactions thing in the burner come
Reduce.
A kind of approach of temperature for controlling burner, which is related to, is pre-mixed fuel and air, to produce before combustion
Fuel air mixture.The approach may include the axially staged of fuel injection, wherein the first fuel air mixture is in burner
First or primary combustion zone at injection and light, to produce the main flow of high-energy combustion gas, and wherein the second fuel-air
Mixture is in main flow of the primary combustion zone downstream injection to high-energy combustion gas and mixed.Specifically, the second combustion
Material air mixture becomes to carry the master of high-energy combustion gas to be referred to alternatively as before the approach of axially staged injection lights
Stream.
The possibility of the complete burning of axially staged injection increase available fuel, this then reduces air emissions.
Bypath air for head portion being used in axially staged injector, from burner changes head end temperature, with
The carbon monoxide during part load operation is reduced to produce.In order to realize with make fuel injection be axially classified it is associated with
The benefit of upper description, the second air and fuel mixture must be sufficiently mixed or blend before being ejected into burner.Close
Continue in well-mixed challenge.
The content of the invention
Aspect and advantage are explained below in the following description, or can from be described as it will be evident that or can by practice
Study.
One embodiment of the disclosure is a kind of fuel injector assembly.Fuel injector assembly includes limiting combustion therein
Expect the shield of manifold.Fuel manifold is fluidly coupled to burning line, to receive from it fuel.Fuel injector assembly also includes
Central body is operably coupled to shield by central body and multiple stators, the plurality of stator.Multiple stators with each other along week
To interval, to limit at least one path therebetween, its transmission is passed through for air.Each in multiple stators has and combustion
At least one outlet opening of at least one passage in manifold and at least one path is expected, for fuel at least one
Releasing in individual path, for being mixed with air.Fuel injector outlet is limited by the inwall of fuel injector assembly, and fixed
Position is guided out fuel injector assembly into by fuel air mixture.
Another embodiment of the present disclosure is related to a kind of axially staged fuel injection system.System includes burning line, its
The pre- aperture in burning line is arranged at the position for being included in the outlet upstream of burning line.Pre- aperture includes being less than pre- aperture
The aperture cross section in the main cross section region of the fuel of upstream.System also includes fuel injector assembly.Fuel injector assembly
Shield including limiting fuel manifold therein, wherein fuel manifold are in fluid communication with burning line, to receive from it fuel.Combustion
Material ejector component also includes central body, and the central body was limited along leading to that the whole length of central body is axially extended
Road, for purging air-flow to be transmitted through into it.Central body is operably coupled to shield by multiple stators.In multiple stators
Each stator and circumferentially-adjacent stator are circumferentially spaced, to limit at least one path therebetween, and its is passed through for air
Send.Each in multiple stators includes at least one outlet opening with fuel manifold and at least one passage.It is (many
It is individual) fuel is released at least one path by outlet opening, for being mixed with air.Fuel injector assembly also includes fuel and sprayed
Emitter is exported, and it is limited by the inwall of fuel injector assembly, and is positioned to fuel air mixture being guided out fuel spray
Emitter assemblies, and the inwall positioned at fuel injector outlet nearside zone of convergence.
Another embodiment includes a kind of gas-turbine unit.Gas-turbine unit includes compressor, turbine, and combustion
Burner, it includes axially staged fuel injector assembly.Fuel injector assembly includes limiting the shield of fuel manifold therein
Cover.Fuel manifold is fluidly coupled to burning line, to receive from it fuel.Fuel injector assembly also include central body and
Central body is operably coupled to shield by multiple stators, the plurality of stator.Each stator and circumferential phase in multiple stators
Adjacent stator is circumferentially spaced, to limit at least one path therebetween, and its transmission is passed through for air.In multiple stators
Each have with fuel manifold be in fluid communication at least one outlet opening, for fuel to the releasing at least one path,
For being mixed with air.Fuel injector assembly also includes fuel injector outlet, and it is limited by the inwall of fuel injector assembly
It is fixed, and be positioned to fuel air mixture being guided out fuel injector assembly.
A kind of fuel injector assembly of technical scheme 1., it includes：
Shield, it limits fuel manifold therein, wherein the fuel manifold is fluidly coupled to burning line, to receive from it
Fuel；
Central body；
Multiple stators, the central body is operably coupled to the shield by it, the multiple stator with each other circumferentially
Interval, to limit at least one path therebetween, pass through in its transmission, the multiple stator for air each have with
At least one outlet opening of the fuel manifold and at least one passage at least one described path, for institute
Fuel is stated to the releasing at least one described path, for being mixed with the air；And
Fuel injector outlet, it is limited by the inwall of the fuel injector assembly, and is positioned to mix fuel-air
Thing is guided out the fuel injector assembly.
Fuel injector assembly of the technical scheme 2. according to technical scheme 1, it is characterised in that the burning line
Including main cross section region and the pre- orifice structure being disposed therein, the pre- orifice structure has less than the main cross section region
Aperture cross section.
Fuel injector assembly of the technical scheme 3. according to technical scheme 1, it is characterised in that the central body
The passage along its whole length is limited, for purging air to be sent towards the fuel injector outlet.
Fuel injector assembly of the technical scheme 4. according to technical scheme 1, it is characterised in that the fuel injection
Device assembly also includes the zone of convergence of the inwall positioned at the fuel injector outlet nearside.
Fuel injector assembly of the technical scheme 5. according to technical scheme 4, it is characterised in that the injector
Radially innermost surface is coated with thermal barrier coating.
Fuel injector assembly of the technical scheme 6. according to technical scheme 1, it is characterised in that the central body
Outlet end regions be at an angle of radially inward.
Fuel injector assembly of the technical scheme 7. according to technical scheme 1, it is characterised in that the shield includes
Circular geometry.
Fuel injector assembly of the technical scheme 8. according to technical scheme 7, it is characterised in that the fuel manifold
In the shield circumferentially.
A kind of axially staged fuel injection system of technical scheme 9., it includes：
Burning line, it is included in the pre- hole being arranged at the position of the outlet upstream of the burning line in the burning line
Mouthful, the pre- aperture has the aperture cross section in the main cross section region of the fuel less than the pre- aperture upstream；
Fuel injector assembly, it includes：
Shield, it limits fuel manifold therein, wherein the fuel manifold is in fluid communication with the burning line, to be connect from it
Receive fuel；
Central body, the central body limits the passage axially extended along the whole length of the central body, is used for
Purging air-flow is transmitted through it；
Multiple stators, the central body is operably coupled to the shield by it, the multiple stator with each other circumferentially
Interval, to limit at least one path therebetween, pass through in its transmission, the multiple stator for air each have with
At least one outlet opening of the fuel manifold and at least one passage, for the fuel to it is described at least
Releasing in one path, for being mixed with the air；
Fuel injector outlet, it is limited by the inwall of the fuel injector assembly, and is positioned to mix fuel-air
Thing is guided out the fuel injector assembly；And
The zone of convergence of the inwall, it is located at the fuel injector outlet nearside.
Axially staged fuel injector system of the technical scheme 10. according to technical scheme 9, it is characterised in that institute
The radially innermost surface for stating fuel injector assembly is coated with thermal barrier coating.
Axially staged fuel injector system of the technical scheme 11. according to technical scheme 9, it is characterised in that institute
The port of export for stating central body is at an angle of radially inward.
Axially staged fuel injector system of the technical scheme 12. according to technical scheme 9, it is characterised in that institute
Stating shield includes circular geometry.
Axially staged fuel injector system of the technical scheme 13. according to technical scheme 12, it is characterised in that
The fuel manifold in the shield circumferentially.
A kind of gas-turbine unit of technical scheme 14., it includes：
Compressor；
Turbine；And
Burner, it includes axially staged fuel injector assembly, and the fuel injector assembly includes：
Shield, it limits fuel manifold therein, wherein the fuel manifold is fluidly coupled to burning line, to receive from it
Fuel；
Central body；
Multiple stators, the central body is operably coupled to the shield by it, the multiple stator with each other circumferentially
Interval, to limit at least one path therebetween, pass through in its transmission, the multiple stator for air each have with
At least one outlet opening that the fuel manifold is in fluid communication, for the fuel to the releasing at least one described path,
For being mixed with the air；And
Fuel injector outlet, it is limited by the inwall of the fuel injector assembly, and is positioned to mix fuel-air
Thing is guided out the fuel injector assembly.
Gas-turbine unit of the technical scheme 15. according to technical scheme 14, it is characterised in that the cartridge
Line includes main cross section region and the pre- orifice structure being disposed therein, and the pre- orifice structure, which has, is less than the main cross section region
Aperture cross section.
Gas-turbine unit of the technical scheme 16. according to technical scheme 14, it is characterised in that the center sheet
Body limits the passage along its whole length, for sweep air flow to be sent towards the fuel injector outlet.
Gas-turbine unit of the technical scheme 17. according to technical scheme 14, it is characterised in that the combustion gas whirlpool
Turbine also includes the convergence of the inwall of the fuel injector assembly positioned at the fuel injector outlet nearside
Region.
Gas-turbine unit of the technical scheme 18. according to technical scheme 17, it is characterised in that the injector
Radially innermost surface be coated with thermal barrier coating.
Gas-turbine unit of the technical scheme 19. according to technical scheme 14, it is characterised in that the fuel spray
The shield of emitter assemblies includes circular geometry.
Gas-turbine unit of the technical scheme 20. according to technical scheme 19, it is characterised in that the fuel discrimination
Pipe circumferentially fully extends in the shield.
Those skilled in the art will more preferably recognize the feature and aspect of such embodiment after specification is checked, and
Other features and aspect.
Brief description of the drawings
The complete and open disclosure of various embodiments including its optimal mode for those skilled in the art is in bag
More specifically illustrated in the remainder for including specification referring to the drawings, in the figure：
Fig. 1 is the functional block diagram of the exemplary gas turbine for the various embodiments that may be incorporated into the disclosure；
Fig. 2 is the simplification side cross-sectional view of the exemplary burner for the various embodiments that such as may be incorporated into the disclosure；
Fig. 3 be according to the disclosure at least one in terms of burner as shown in Figure 2 fuel injector assembly section
View；
Fig. 4 is the birds-eye perspective of Fig. 3 fuel injector assembly；
Fig. 5 is the section view of Fig. 3 fuel injector assembly；And
The cross-sectional end view of the Fig. 3 of Fig. 6 for installation in the burner fuel injector assembly.
List of parts
10 gas turbines
12 entrance zone, threshold zones
14 compressors
16 burners
18 turbines
20 exhaust sections
22 axles
24 air
26 compressed airs
28 fuel
30 burning gases
32 shells
34 high pressure bins
36 end caps
38 head portions
40 primary fuel nozzles
42 pipelines/bushing
44 first combustion zones
46 second combustion zones
48 center lines
50 hot gas paths
52 entrances-turbine
54 flowings/impact sleeve pipe
56 annularly flow paths
58 primary combustion air-flows/main flow
100 axially staged fuel injection systems
102 fuel injector assemblies
104 fuel injectors
106 burning lines
108 ingress ports-fuel injector assembly
110 pre- orifice structures
112 pre- apertures
114 airhoods
116 shields
118 central bodies
120 stators
122 fuel manifolds
124 paths
126 chambers
128 outlet openings
130 fuel injector outlets
132 inwalls
134 radial convergence regions
136 radially innermost surfaces
138 TBC
140 outlet end regions
142 passages
144 entrances-passage
146 purge holes
148 Cooling Holes
150 is raised.
Embodiment
The present embodiment of the disclosure is reference will now be made in detail to now, and its one or more example is shown in the drawings.Retouch in detail
State and used numeral and alphabetical designation to represent the feature in accompanying drawing.The accompanying drawing label similar or similar with description is used to represent
The similar or similar part of the disclosure.
As used in this article, term " first ", " second " and " the 3rd " can be interchangeably used, by a component
Distinguished with another, and be not intended to the position for representing individual member or importance.Term " upstream " and " downstream " refer to phase
For the relative direction of the fluid stream in fluid passage.For example, " upstream " refers to the direction of fluid stream certainly, and " downstream " refers to stream
The direction that body is flow to.Term " radially " refers to the relative direction for the longitudinal center line for being approximately perpendicular to particular elements, and uses
Language " axially " refers to be roughly parallel to and/or is coaxially aligned in the relative direction of the longitudinal center line of particular elements.
Term used herein is not intended to limitation for only describing the purpose of specific embodiment.As made herein
, singulative " one ", " one " and "the" are intended to also include plural form, unless context is clearly dictated otherwise.Also
It will be appreciated that term " including (comprises) " and/or " including (comprising) " represent when in for this specification
The feature of narration, integer, step, operation, the presence of element and/or component, but exclude and exist or add one or more
Individual further feature, integer, step, operation, element, component and/or their group.
Each example is provided via explaination, without limiting.In fact, will become apparent to those skilled in the art
It is that can make remodeling and modification, without departing from its scope or spirit.For example, be illustrated or described as the part of one embodiment
Feature can be used in another embodiment producing another embodiment.It is therefore intended that appended right is included into disclosure covering
It is required that and such remodeling in the range of their equivalent and modification.Although the exemplary embodiment of the disclosure will be for diagram
Purpose is described generally under the background for the burner of continental rise power generation gas turbine, but those skilled in the art will easily recognize
Know, embodiment of the disclosure can be applied to the burner of any types or species for turbine, and be not limited to use in
The burner or combustion system of continental rise power generation gas turbine, except clearly being described in non-claimed.
Referring now to accompanying drawing, Fig. 1 shows the schematic diagram of exemplary gas turbine 10.Gas turbine 10 generally includes entrance
Section 12, the compressor 14 for being arranged on the downstream of entrance zone, threshold zone 12, at least one burner 16 for being arranged on the downstream of compressor 14, set
The turbine 18 in the downstream of burner 16 is put, and is arranged on the exhaust section 20 in the downstream of turbine 18.In addition, gas turbine 10 can be wrapped
One or more axles 22 are included, compressor 14 is connected in turbine 18 by it.
During operation, air 24 flows through entrance zone, threshold zone 12 and into compressor 14, and wherein air 24 is by gradually
Ground is compressed, therefore compressed air 26 is provided to burner 16.At least a portion of compressed air 26 is in burner 16 with firing
Material 28 is mixed and burned, to produce burning gases 30.Burning gases 30 are flow in turbine 18 from burner 16, wherein energy
(kinetic energy and/or heat energy) is transferred to rotor blade (not shown) from burning gases 30, therefore causes axle 22 to rotate.Mechanical rotation energy
Various purposes can be then used in, electricity is such as energized and/or generate to compressor 14.Leaving the burning gases 30 of turbine 18 can then pass through
Discharged by exhaust section 20 from gas turbine 10.
As shown in Figure 2, burner 16 can at least in part be wrapped by shell 32 (such as compressor discharge shell).Shell 32
High pressure bins 34 can be at least partially defined, it wraps the various components of burner 16 at least in part.High pressure bins 34 can be with
Compressor 14 (Fig. 1) is in fluid communication, to receive from it compressed air 26.End cap 36 can be attached to shell 32.In particular implementation
In example, the forward part and end cap 36 of shell 32 can at least partially define head end volume or the part 38 of burner 16.Specific
In embodiment, head portion 38 is in fluid communication with high pressure bins 34 and/or compressor 14.
One or more primary fuel nozzles 40 extend axially downstream from end cap 36.One or more bushings or
Pipeline 42 can at least partially define the primary or the first burning or reaction zone 44 for first fuel air mixture that burns, and
And/or person can at least partially define the second burning or reaction zone 46, its longitudinal center line 48 from first on burner 16
Combustion zone 44 is formed axially downstream.(multiple) bushing 42 is generally limited from (multiple) primary fuel nozzles 40 to turbine 18
The hot gas path 50 of the entrance 52 of (Fig. 1).(multiple) bushing 42 is formed as so as to including tapered or transition portion.
In at least one embodiment, burner 16 includes axially staged fuel injection system 100.Axially staged combustion
Expect that spraying system 100 includes at least one fuel injector assembly 102, it is on longitudinal center line 48 and (multiple) primary fuel
Nozzle 40 is axially staged or is spaced.Fuel injector assembly 102 be arranged on the downstream of (multiple) primary fuel nozzles 40 and
The upstream of entrance 52 of turbine 18.
Fuel injector assembly 102 extends through (multiple) bushing 42, and is in fluid communication with hot gas path 50.Fuel
Injector assembly 102 can have the opening flushed with the surface of (multiple) bushing 42 (being shown in such as Fig. 3), or alternately, combustion
Material ejector component 102 can project through (multiple) bushing 42 towards the second combustion zone 46.It will be appreciated that fuel injector group
Part 102 may also extend through flowing or impact sleeve pipe 54, and it wraps (multiple) bushing 42 at least in part.In this configuration, flow
Dynamic sleeve pipe 54 and (multiple) bushing 42 can limit annularly flow path 56 therebetween.Annularly flow path 56 can provide or limit height
Press the flow path between bin 34 and the head portion 38 of burner 16.
It is contemplated that a large amount of fuel injector assembly 102 (including two, three, four, five, or more a fuel spray
Emitter assemblies 102) it can be used in single burner 16.Fuel injector assembly 102 can around (multiple) bushing 42 periphery phase
Etc. ground interval, or can be with some other spacing intervals, to accommodate pillar or other mould components.
In order to which simple, axially staged fuel injection system 100 is referred to as and is illustrated herein as with fuel injection
Device assembly 102, it is in the single-stage or axial plane in the downstream of primary combustion zone 44.It is contemplated, however, that, axially staged fuel
Spraying system 100 may include the level of two axially spaced-aparts of fuel injector assembly 102.For example, first group of fuel injector group
Part 102 and second group of fuel injector assembly 102 can along (multiple) bushing 42 with it is axially spaced each other.
In operation, (it is by air and from primary fuel nozzles for the primary combustion air-flow or main flow 58 of burning gases 30
The burning of 40 fuel is produced) region in primary combustion zone 44 to hot gas path 50 is travelled across, it is in fuel injector
The radially inner side of component 102 and in the upstream of entrance 52 of turbine 18.Second fuel air mixture is by one or more fuel
Injector assembly 102 sprays, and penetrates the main flow 58 of arriving.Fuel supplied to fuel injector assembly 102 is entering whirlpool
Burnt before wheel 18 in the second combustion zone 46.
Fig. 3 illustrates in greater detail the fuel injector assembly 102 according at least one embodiment of the disclosure.Fuel injection
Device assembly 102 includes being fluidly coupled to the fuel injector 104 of burning line or conduit 106.Fuel injector 104 is via combustion
The ingress port 108 of material ejector component 102 receives fuel via burning line 106.The cross section of burning line 106 can edge
The change of its length, wherein smallest cross-sectional region is the part of pre- orifice structure 110, it, which has, is located at the upstream of ingress port 108
The pre- aperture 112 of at least one fuel (see Fig. 5).Pre- aperture 112 is formed as ensuring, the mobilization dynamic in burning line 106
It is insensitive to upstream pressure pulse or flowing change.In at least one embodiment, fuel injector assembly 102 may also include guarantor
Airhood 114 is protected, it is arranged on burning line 106 and the radial outside of fuel injector 104, as discussed further below.
Fig. 4 and Fig. 5 illustrate in greater detail fuel injector 104.As shown in Fig. 4 and Fig. 5, the wrapping of shield 116 center
Body 118 and a large amount of stators 120, a large amount of stators 120 extend between shield 116 and central body 118 and operatively joined
Connect them.In one embodiment, shield 116 extends into circle.As shown in Figure 5, shield 116, which is limited, is referred to as fuel discrimination
The hollow inner region of pipe 122.Fuel manifold 122 is fluidly coupled to burning line 106 so that fuel manifold 122 is received from it
Fuel.In one embodiment, fuel manifold 122 fully extends around shield 116, to form 360 degree of fuel manifolds 122.
Fuel is sent to stator 120 from manifold 122.As shown in Figure 4, stator 120 with it is circumferentially spaced each other, to limit therebetween
A large amount of paths 124.In addition, fuel manifold 122 may include one or more openings 152 (Fig. 6) between stator 120, fuel
One or more openings 152 can be also carried through.Path 124 allows the air of compression to be transmitted through it, for carrying out self-conductance
Leaf 120 and alternatively from manifold apertures 152 fuel mixing, such as by herein from describe recognize.
In at least one embodiment as shown in Figure 5, at least one in stator 120 limits chamber 126 therein, its
The fuel from fuel manifold 122 is received in a uniformly distributed manner, and particularly fuel manifold 122 surrounds shield 116 wherein
In the embodiment of 360 degree of extension.Fuel flows through one or more outlet openings of each corresponding stator 120 from chamber 126
128, for sending to path 124.In path 124, fuel is mixed with being directed across its compressed air.Stator 120 has
Geometry, the vortex of its promotion compressed air and promotion flow through the mixing of the fuel air mixture of path 124.Rotation
Vortex is guided towards fuel injector outlet 130, and is finally guided out fuel injector outlet 130, fuel injector outlet
130 are limited by the inwall 132 of fuel injector assembly 102.Fuel air mixture is guided out combustion by fuel injector outlet 130
Material ejector 104 and it is directed in the second combustion zone 46.
Inwall 132 (it can be integrated with shield 116) has in the radial convergence region of the nearside of fuel injector outlet 130
134, to prevent non-return combustion, and by being at least partially formed Venturi tube to accelerate fuel air mixture to leave fuel injection
Device exports 130 to promote fuel air mixture to the more preferable spray penetration in the second combustion zone 46.In certain embodiments, it is interior
The radially innermost surface 136 of wall 132 can be coated with thermal barrier coating 138.Central body 118 can central body 118 the port of export
It is tapered radially inward at region 140, at least partially define the fuel of the inwall 132 on fuel injector assembly 102
Air mixture path.
In at least one embodiment, passage 142 is along the central axis or longitudinal center line of central body 118 and edge
The whole length extension of central body 118, to limit the path through it.In operation, the sky from high pressure bins 34
Gas is directed in airhood 114 (Fig. 3) and into the radial outer end of injector 104.In one embodiment, air via
Entrance 144 flows through passage 142 in a radially inward direction, and entrance 144 is limited by central body 118 and is arranged on fuel spray
At the radially-outer surface of emitter 104 or in its nearside.Passage 142 is by compressed air from entrance 144 towards fuel injector outlet
130 send, to purge exit region (that is, to push fuel air mixture to outlet 130), thus reduce and pass through fuel injection
The possibility of the backfire of device assembly 102.
In certain embodiments, the entrance 144 of passage 142 can be provided with purge hole or entrance 146 transverse to passage 142.
Passage 142 can at entrance 144 closure or openness.As described in above with respect to passage 142, air is flowable through laterally purging
Hole 146, it can be limited and/or circumferentially spaced around the entrance 144 of central body 118.
Fig. 6 is shown such as the part for being positioned at exemplary cartridge 142 and exemplary flow or a part for impact sleeve pipe 54
Between fuel injector 104.As shown in Figure 6, fuel injector 104 is mountable to bushing 42 and/or impact sleeve pipe 54
In one or both.In a particular embodiment, Cooling Holes or path 148 are located in injector installation base 150, will cooling
Air is guided towards fuel injector 104, for cooling down it.For example, cooling air can be turned to from annular channels 56 (Fig. 2).
The embodiment of fuel injector assembly 102 described herein provides the NOx productions and reduction CO with reduction
The many advantages that can be associated.This passes through for being mixed with compressed air by the homogeneous fuel of fuel manifold 122 is distributed come real
It is existing.It is blended in path and performs, and guide vane structure causes the vortex of fuel air mixture before being ejected into burner
Stream.Vortex enhances the mixing in fuel injector 104 and mixed with the cross-current of main or primary combustion gas stream 48, with fast
Flame temperature is reduced fastly, thus reduces NOx.
The written description, to disclose of the invention (including optimal mode), and also makes those skilled in the art using example
Can put into practice the present invention (including manufacture and using any device or system and perform any method being incorporated to).The present invention's can
The scope of the claims is defined by the claims, and may include other examples that those skilled in the art expect.If these other realities
Example includes the structural detail different not from the literal language of claim, or if these other examples include and claim
Equivalent structural elements of the literal language without marked difference, then these other examples be intended within the scope of the claims.
Claims (10)
1. a kind of fuel injector assembly (102), it includes：
Shield (116), it limits fuel manifold (122) therein, wherein the fuel manifold (122) is fluidly coupled to fuel
Pipeline (106), to receive from it fuel；
Central body (118)；
Multiple stators (120), the central body (118) is operably coupled to the shield (116) by it, the multiple to lead
Leaf (120) with it is circumferentially spaced each other, to limit at least one path (124) therebetween, its transmission, institute are passed through for air
State in multiple stators (120) each have with the fuel manifold (122) and at least one described path (124) at least
At least one outlet opening (128) that one path (124) is in fluid communication, for the fuel at least one described path
(124) releasing in, for being mixed with the air；And
Fuel injector outlet (130), it is limited by the inwall (132) of the fuel injector assembly (102), and is positioned to
Fuel air mixture is guided out the fuel injector assembly (102).
2. fuel injector assembly (102) according to claim 1, it is characterised in that the burning line (106) includes
Main cross section region and pre- aperture (112) structure (110) being disposed therein, pre- aperture (112) structure (110), which has, to be less than
The aperture cross section in the main cross section region.
3. fuel injector assembly (102) according to claim 1, it is characterised in that the central body (118) limits
Along the passage (144) of its whole length, for purging air to be sent towards the fuel injector outlet (130).
4. fuel injector assembly (102) according to claim 1, it is characterised in that the fuel injector assembly
(102) zone of convergence (134) of the inwall (132) positioned at the fuel injector outlet (130) nearside is also included.
5. fuel injector assembly (102) according to claim 4, it is characterised in that the fuel injector assembly
(102) radially innermost surface (136) is coated with thermal barrier coating (138).
6. fuel injector assembly (102) according to claim 1, it is characterised in that central body (118) go out
Mouth end regions (140) are at an angle of radially inward.
7. fuel injector assembly (102) according to claim 1, it is characterised in that the shield (116) includes circle
Geometry.
8. fuel injector assembly (102) according to claim 7, it is characterised in that the fuel manifold (122) is in institute
State in shield (116) circumferentially.
9. a kind of axially staged fuel injection system (100), it includes：
Burning line (106), it, which is included at the position of the outlet upstream of the burning line (106), is arranged on the cartridge
Pre- aperture in line (106), the pre- aperture (112) has the burning line less than pre- aperture (112) upstream
(106) the aperture cross section in main cross section region；
Fuel injector assembly (102), it includes：
Shield (116), it limits fuel manifold (122) therein, wherein the fuel manifold (122) and the burning line
(106) it is in fluid communication, to receive from it fuel；
Central body (118), whole length of central body (118) restriction along the central body (118) is vertically
The passage (144) of extension, for purging air-flow to be transmitted through into it；
Multiple stators (120), the central body (118) is operably coupled to the shield (116) by it, the multiple to lead
Leaf (120) with it is circumferentially spaced each other, to limit at least one path (124) therebetween, its transmission, institute are passed through for air
Each stated in multiple stators (120) has and the fuel manifold (122) and at least one described path (124) fluid communication
At least one outlet opening (128), for the fuel to the releasing at least one described path (124), for it is described
Air is mixed；
Fuel injector outlet (130), it is limited by the inwall (132) of the fuel injector assembly (102), and is positioned to
Fuel air mixture is guided out the fuel injector assembly (102)；And
The zone of convergence (134) of the inwall (132), it is located at the fuel injector outlet (130) nearside.
10. axially staged fuel injector system (100) according to claim 9, it is characterised in that the fuel spray
The radially innermost surface (136) of emitter assemblies (102) is coated with thermal barrier coating (138).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/073,694 US20170268786A1 (en) | 2016-03-18 | 2016-03-18 | Axially staged fuel injector assembly |
| US15/073694 | 2016-03-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107202339A true CN107202339A (en) | 2017-09-26 |
Family
ID=58267028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710157101.3A Pending CN107202339A (en) | 2016-03-18 | 2017-03-16 | Axially Staged Fuel Injector Assembly |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20170268786A1 (en) |
| EP (1) | EP3220055A1 (en) |
| JP (1) | JP2017172953A (en) |
| CN (1) | CN107202339A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111380075A (en) * | 2018-12-25 | 2020-07-07 | 安萨尔多能源瑞士股份公司 | Injector head for a gas turbine combustor |
| CN113310071A (en) * | 2021-06-16 | 2021-08-27 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11137144B2 (en) * | 2017-12-11 | 2021-10-05 | General Electric Company | Axial fuel staging system for gas turbine combustors |
| US10982856B2 (en) | 2019-02-01 | 2021-04-20 | Pratt & Whitney Canada Corp. | Fuel nozzle with sleeves for thermal protection |
| KR102138013B1 (en) * | 2019-05-30 | 2020-07-27 | 두산중공업 주식회사 | Combustor with axial fuel staging and gas turbine including the same |
| KR102138016B1 (en) * | 2019-06-11 | 2020-07-27 | 두산중공업 주식회사 | Combustor with axial fuel staging and gas turbine including the same |
| KR102583225B1 (en) | 2022-02-07 | 2023-09-25 | 두산에너빌리티 주식회사 | Micromixer and gas turbine comprising the same |
| KR102583226B1 (en) | 2022-02-07 | 2023-09-25 | 두산에너빌리티 주식회사 | Micromixer with multi-stage fuel supply and gas turbine including same |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
| US5675971A (en) * | 1996-01-02 | 1997-10-14 | General Electric Company | Dual fuel mixer for gas turbine combustor |
| US6986255B2 (en) * | 2002-10-24 | 2006-01-17 | Rolls-Royce Plc | Piloted airblast lean direct fuel injector with modified air splitter |
| US20110244410A1 (en) * | 2010-03-30 | 2011-10-06 | General Electric Company | Pilot system for combustors |
| CN103717971B (en) * | 2011-08-11 | 2015-09-02 | 通用电气公司 | For the system of burner oil in gas-turbine unit |
| US9310078B2 (en) * | 2012-10-31 | 2016-04-12 | General Electric Company | Fuel injection assemblies in combustion turbine engines |
| US9021781B2 (en) * | 2013-01-04 | 2015-05-05 | General Electric Company | Fuel injector having an ignitor for igniting a combustor of a gas turbine |
| US9551490B2 (en) * | 2014-04-08 | 2017-01-24 | General Electric Company | System for cooling a fuel injector extending into a combustion gas flow field and method for manufacture |
-
2016
- 2016-03-18 US US15/073,694 patent/US20170268786A1/en not_active Abandoned
-
2017
- 2017-03-10 JP JP2017045536A patent/JP2017172953A/en active Pending
- 2017-03-13 EP EP17160602.3A patent/EP3220055A1/en not_active Withdrawn
- 2017-03-16 CN CN201710157101.3A patent/CN107202339A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111380075A (en) * | 2018-12-25 | 2020-07-07 | 安萨尔多能源瑞士股份公司 | Injector head for a gas turbine combustor |
| CN111380075B (en) * | 2018-12-25 | 2023-04-18 | 安萨尔多能源瑞士股份公司 | Injector head for a gas turbine combustor |
| CN113310071A (en) * | 2021-06-16 | 2021-08-27 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3220055A1 (en) | 2017-09-20 |
| US20170268786A1 (en) | 2017-09-21 |
| JP2017172953A (en) | 2017-09-28 |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170926 |
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| WD01 | Invention patent application deemed withdrawn after publication |